Airworthiness Directives; BAE SYSTEMS (Operations) Limited Model ATP Airplanes, 8467-8471 [2010-3470]

Download as PDF Federal Register / Vol. 75, No. 37 / Thursday, February 25, 2010 / Rules and Regulations Office. The AMOC approval letter must specifically reference this AD. (3) An AMOC that provides an acceptable level of safety may be used for any repair required by this AD, if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Los Angeles ACO, to make those findings. For a repair method to be approved, the repair must meet the certification basis of the airplane and the approval must specifically refer to this AD. Material Incorporated by Reference (i) You must use Boeing Alert Service Bulletin MD90–53A031, dated April 10, 2009, to do the actions required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, 3855 Lakewood Boulevard, MC D800–0019, Long Beach, California 90846– 0001; telephone 206–544–5000, extension 2; fax 206–766–5683; e-mail dse.boecom@boeing.com; Internet https:// www.myboeingfleet.com. (3) You may review copies of the service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information on the availability of this material at the FAA, call 425–227–1221 or 425–227–1152. (4) You may also review copies of the service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: https://www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on February 16, 2010. Stephen P. Boyd, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2010–3469 Filed 2–24–10; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2010–0130; Directorate Identifier 2009–NM–087–AD; Amendment 39–16214; AD 2010–05–05] jlentini on DSKJ8SOYB1PROD with RULES RIN 2120–AA64 Airworthiness Directives; BAE SYSTEMS (Operations) Limited Model ATP Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). VerDate Nov<24>2008 16:14 Feb 24, 2010 Jkt 220001 ACTION: Final rule; request for comments. SUMMARY: We are adopting a new airworthiness directive (AD) for the products listed above that would supersede an existing AD. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: A review of the results of the final fuselage fatigue test identified the need for additional and revised safety-related fatigue- and environmental inspections for the fuselage. These additional tasks were introduced by Service Bulletin (SB) ATP–51–002 * * *. As it was determined that these inspections were necessary to maintain the structural integrity of the aeroplane, EASA AD 2006–0090 [which corresponds to FAA AD 2007–15–08] was issued * * *. Since the original Issue of the SB, three revisions have been published. Revision 1 of the SB included only editorial changes. Revision 2 of the SB corrected the fuselage frame designations in Parts 50 and 50A and extended the allowable time before initial inspection. In addition, the repeat inspection interval in Part 43 of the SB was reduced. In the latest Revision 3 of the SB, the grace period for the initial inspection in Part 50 has been clarified. * * * * * The unsafe condition is fatigue cracking of certain structural elements, which could result in reduced structural integrity of the airplane and consequent rapid decompression of the airplane. This AD requires actions that are intended to address the unsafe condition described in the MCAI. DATES: This AD becomes effective March 12, 2010. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of March 12, 2010. On September 21, 2006 (71 FR 52418, September 6, 2006), the Director of the Federal Register approved the incorporation by reference of a certain other publication listed in this AD. We must receive comments on this AD by April 12, 2010. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: (202) 493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 8467 30, West Building Ground Floor, Room W12–40, 1200 New Jersey Avenue, SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (800) 647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Todd Thompson, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–1175; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: Discussion On July 15, 2007, we issued AD 2007– 15–08, Amendment 39–15137 (72 FR 40230, July 24, 2007). That AD required actions intended to address an unsafe condition on the products listed above. Since we issued AD 2007–15–08, the European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA Airworthiness Directive 2009–0074, dated March 31, 2009 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: A review of the results of the final fuselage fatigue test identified the need for additional and revised safety-related fatigue- and environmental inspections for the fuselage. These additional tasks were introduced by Service Bulletin (SB) ATP–51–002, which supplemented and in some cases revised those previously published in the Aircraft Maintenance Manual (AMM) Chapter 05–10– 17 and the Maintenance Review Board Report (MRBR). As it was determined that these inspections were necessary to maintain the structural integrity of the aeroplane, EASA AD 2006–0090 [which corresponds to FAA AD 2007–15–08] was issued to require the inspections and, depending on findings, corrective actions as defined in BAE Systems (Operations) Limited SB ATP–51–002 (the SB) at original issue. Since the original Issue of the SB, three revisions have been published. Revision 1 of the SB included only editorial changes. Revision 2 of the SB corrected the fuselage frame designations in Parts 50 and 50A and extended the allowable time before initial E:\FR\FM\25FER1.SGM 25FER1 8468 Federal Register / Vol. 75, No. 37 / Thursday, February 25, 2010 / Rules and Regulations inspection. In addition, the repeat inspection interval in Part 43 of the SB was reduced. In the latest Revision 3 of the SB, the grace period for the initial inspection in Part 50 has been clarified. Fatigue tasks in Parts 1 through 50 of the SB, i.e. those without an ‘‘A’’ suffix, have now been replicated in AMM Chapter 05–10–17 and MRBR Section 6. In addition, environmental tasks, those identified with an ‘‘A’’ suffix, have now been replicated in MRBR Section 6. For the reasons described above, this AD retains the requirements of EASA AD 2006– 0090, which is superseded, and requires the accomplishment of the inspections and, depending on findings, corrective actions as defined in BAE Systems (Operations) Limited SB ATP–51–002 at Revision 3. The unsafe condition is fatigue cracking of certain structural elements, which could result in reduced structural integrity of the airplane and consequent rapid decompression of the airplane. The corrective actions include repairing cracking and corrosion, and depending on findings, repairing or replacing damaged components. You may obtain further information by examining the MCAI in the AD docket. different words from those in the MCAI to ensure the AD is clear for U.S. operators and is enforceable. In making these changes, we do not intend to differ substantively from the information provided in the MCAI and related service information. We might also have required different actions in this AD from those in the MCAI in order to follow FAA policies. Any such differences are highlighted in a NOTE within the AD. Change to Existing AD This AD retains all requirements of AD 2007–15–08. Since AD 2007–15–08 was issued, the AD format has been revised, and certain paragraphs have been rearranged. As a result, the corresponding paragraph identifiers have changed in this AD, as listed in the following table: REVISED PARAGRAPH IDENTIFIERS Requirement in AD 2007–15–08 Corresponding requirement in this AD paragraph (f) paragraph (g) paragraph (h) paragraph (i) paragraph (j) paragraph (k) paragraph (g). paragraph (h). paragraph (i). paragraph (j). paragraph (k). paragraph (l). Relevant Service Information BAE SYSTEMS (Operations) Limited has issued Service Bulletin ATP–51– 002, Revision 3, dated April 3, 2008. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. FAA’s Determination and Requirements of This AD jlentini on DSKJ8SOYB1PROD with RULES This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are issuing this AD because we evaluated all pertinent information and determined the unsafe condition exists and is likely to exist or develop on other products of the same type design. There are no products of this type currently registered in the United States. However, this rule is necessary to ensure that the described unsafe condition is addressed if any of these products are placed on the U.S. Register in the future. Differences Between the AD and the MCAI or Service Information We have reviewed the MCAI and related service information and, in general, agree with their substance. But we might have found it necessary to use VerDate Nov<24>2008 16:14 Feb 24, 2010 Jkt 220001 FAA’s Determination of the Effective Date Since there are currently no domestic operators of this product, notice and opportunity for public comment before issuing this AD are unnecessary. Comments Invited This AD is a final rule that involves requirements affecting flight safety, and we did not precede it by notice and opportunity for public comment. We invite you to send any written relevant data, views, or arguments about this AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2010–0130; Directorate Identifier 2009–NM–087– AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this AD. We will consider all comments received by the closing date and may amend this AD because of those comments. We will post all comments we receive, without change, to https:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this AD. PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ‘‘Subtitle VII: Aviation Programs,’’ describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in ‘‘Subtitle VII, Part A, Subpart III, Section 44701: General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify this AD: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared a regulatory evaluation of the estimated costs to comply with this AD and placed it in the AD docket. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: ■ PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. E:\FR\FM\25FER1.SGM 25FER1 Federal Register / Vol. 75, No. 37 / Thursday, February 25, 2010 / Rules and Regulations § 39.13 [Amended] 2. The FAA amends § 39.13 by removing Amendment 39–15137 (72 FR 40230, July 24, 2007) and adding the following new AD: ■ 2010–05–05 BAE Systems (Operations) Limited: Amendment 39–16214. Docket No. FAA–2010–0130; Directorate Identifier 2009–NM–087–AD. Effective Date (a) This airworthiness directive (AD) becomes effective March 12, 2010. Affected ADs (b) This AD supersedes AD 2007–15–08, Amendment 39–15137. Applicability (c) This AD applies to all BAE Systems (Operations) Limited Model ATP airplanes, certificated in any category. Note 1: This AD requires revisions to certain operator maintenance documents to include new and revised inspections. Compliance with these inspections is required by 14 CFR 91.403(c). For airplanes that have been previously modified, altered, or repaired in the areas addressed by these inspections, the operator may not be able to accomplish the inspections described in the revisions. In this situation, to comply with 14 CFR 91.403(c), the operator must request approval for an alternative method of compliance according to paragraph (q) of this AD. The request should include a description of changes to the required inspections that will ensure the continued damage tolerance of the affected structure. The FAA has provided guidance for this determination in Advisory Circular (AC) 25–1529. jlentini on DSKJ8SOYB1PROD with RULES Subject (d) Air Transport Association (ATA) of America Code: 51: Standard Practices/ Procedures. Reason (e) The mandatory continued airworthiness information (MCAI) states: A review of the results of the final fuselage fatigue test identified the need for additional and revised safety-related fatigue- and environmental inspections for the fuselage. These additional tasks were introduced by Service Bulletin (SB) ATP–51–002, which supplemented and in some cases revised those previously published in the Aircraft Maintenance Manual (AMM) Chapter 05–10– 17 and the Maintenance Review Board Report (MRBR). As it was determined that these inspections were necessary to maintain the structural integrity of the aeroplane, EASA AD 2006–0090 [which corresponds to FAA AD 2007–15–08] was issued to require the inspections and, depending on findings, corrective actions as defined in BAE Systems (Operations) Limited SB ATP–51–002 (the SB) at original issue. Since the original Issue of the SB, three revisions have been published. Revision 1 of the SB included only editorial changes. Revision 2 of the SB corrected the fuselage frame designations in Parts 50 and 50A and VerDate Nov<24>2008 16:14 Feb 24, 2010 Jkt 220001 extended the allowable time before initial inspection. In addition, the repeat inspection interval in Part 43 of the SB was reduced. In the latest Revision 3 of the SB, the grace period for the initial inspection in Part 50 has been clarified. Fatigue tasks in Parts 1 through 50 of the SB, i.e. those without an ‘‘A’’ suffix, have now been replicated in AMM Chapter 05–10–17 and MRBR Section 6. In addition, environmental tasks, those identified with an ‘‘A’’ suffix, have now been replicated in MRBR Section 6. For the reasons described above, this AD retains the requirements of EASA AD 2006– 0090, which is superseded, and requires the accomplishment of the inspections and, depending on findings, corrective actions as defined in BAE Systems (Operations) Limited SB ATP–51–002 at Revision 3. The unsafe condition is fatigue cracking of certain structural elements, which could result in reduced structural integrity of the airplane and consequent rapid decompression of the airplane. The corrective actions include repairing cracking and corrosion, and depending on findings, repairing or replacing damaged components. Compliance (f) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Restatement of Requirements of AD 2006– 18–09, With Revised Compliance Method Airworthiness Limitations Revision Specified in AD 2000–26–10 (g) Within 30 days after February 7, 2001 (the effective date of AD 2000–26–10, Amendment 39–12060, which was superseded by AD 2005–19–03, which was superseded by AD 2007–15–08), revise the Airworthiness Limitations Section (ALS) of the Instructions for Continued Airworthiness according to a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA. Doing the revision specified in paragraph (h) of this AD replaces Chapters 27, 32, 53, and 54 listed in Section 05–10–11 and Chapters 52, 53, 54, 55, and 57 listed in Section 05–10– 17 that are in effect on February 7, 2001, with Chapters 27, 32, 53, and 54 listed in Section 05–10–11, ‘‘Mandatory Life Limitations (Airframe)’’; and Chapters 52, 53, 54, 55, and 57 listed in Section 05–10–17, ‘‘Structurally Significant Items (SSIs)’’; both dated July 15, 2004; of the British Aerospace ATP Aircraft Maintenance Manual (AMM). Doing the revision specified in paragraph (l) of this AD replaces Sections 05–10–12, 05–10–15, and 05–10–17 with the corresponding sections specified in paragraph (l) of this AD. Note 2: Guidance on revising the ALS can be found in Section 05–00–00, dated August 15, 1997, of the British Aerospace ATP AMM, dated October 15, 1999. This section references other chapters of the AMM. The applicable revision level of the referenced chapters is that in effect on February 7, 2001. PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 8469 Airworthiness Limitations Specified in AD 2005–19–03 (h) Within 30 days after September 28, 2005 (the effective date of AD 2005–19–03, Amendment 39–14268, which was superseded by AD 2006–18–09), revise the ALS of the Instructions for Continued Airworthiness according to a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA. Doing the revision specified in paragraph (i) of this AD replaces certain Chapter 52 and 53 tasks listed in Section 05–10–17, ‘‘Structurally Significant Items (SSIs),’’ dated July 15, 2004, of the British Aerospace ATP AMM, with the corresponding Chapter 52 and 53 tasks listed in BAE SYSTEMS (Operations) Limited Service Bulletin ATP–51–002, dated December 20, 2005. Doing the revision specified in paragraph (l) of this AD replaces Chapters 52, 53, 54, 55, and 57 listed in Section 05–10–17 with the corresponding Section 05–10–17 specified in paragraph (l) of this AD. Note 3: Guidance on revising the ALS can be found in Chapters 27, 32, 53, and 54 listed in Section 05–10–11, ‘‘Mandatory Life Limitations (Airframe)’’; and the tasks for Chapters 52, 53, 54, 55, and 57 listed in Section 05–10–17, ‘‘Structurally Significant Items (SSIs)’’; both dated July 15, 2004; of the British Aerospace ATP AMM. These chapters replace the corresponding chapters in Section 05–00–00, dated August 15, 1997, of the British Aerospace ATP AMM as specified in paragraph (g) of this AD. New and Revised Airworthiness Limitations in AD 2006–18–09 (i) Within 30 days after September 21, 2006 (the effective date of AD 2006–18–09), revise the ALS of the Instructions for Continued Airworthiness by incorporating the new and revised tasks for Chapters 52 and 53 as specified in BAE SYSTEMS (Operations) Limited Service Bulletin ATP–51–002, dated December 20, 2005, into the ALS. The revised Chapter 52 and 53 tasks replace the corresponding Chapter 52 and 53 tasks in Section 05–10–17, ‘‘Structurally Significant Items (SSIs),’’ dated July 15, 2004, of the British Aerospace ATP AMM, as specified in paragraph (h) of this AD. (j) Except as provided by paragraph (q) of this AD: After the actions specified in paragraphs (g), (h), and (i) of this AD have been accomplished, no alternative inspections or inspection intervals may be approved for the structural elements specified in the documents listed in paragraphs (g), (h), and (i) of this AD. No Reporting Required (k) Although BAE SYSTEMS (Operations) Limited Service Bulletin ATP–51–002, dated December 20, 2005, specifies to submit certain information to the manufacturer, this AD does not include that requirement. Restatement of Requirements of AD 2007– 15–08, With Revised Compliance Method Revised Limitations (l) Within 30 days after August 8, 2007 (the effective date of AD 2007–15–08), revise the E:\FR\FM\25FER1.SGM 25FER1 8470 Federal Register / Vol. 75, No. 37 / Thursday, February 25, 2010 / Rules and Regulations ALS of the Instructions for Continued Airworthiness according to a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA. Note 4: Guidance on revising the ALS can be found in Section 05–10–12, ‘‘Mandatory Life Limitations (Airframe—Structures),’’ dated January 15, 2007; Section 05–10–15, ‘‘Mandatory Life Limitations (Powerplant/ Engine/APU—Structures),’’ dated January 15, 2007; and Section 05–10–17, ‘‘Structurally Significant Items (SSIs),’’ dated January 15, 2007; of the BAE Systems (Operations) Limited ATP AMM. The revised sections replace the corresponding sections specified in paragraphs (g) and (h) of this AD. (m) Except as provided by paragraph (q) of this AD: After the action specified in paragraph (l) of this AD has been accomplished, no alternative inspections or inspection intervals may be approved for the structural elements specified in the documents listed in paragraph (l) of this AD. New Requirements of This AD Actions (n) Within 30 days after the effective date of this AD: Revise the ALS of the Instructions for Continued Airworthiness by incorporating the inspections specified in BAE SYSTEMS (Operations) Limited Inspection Service Bulletin ATP–51–002, Revision 3, dated April 3, 2008. Doing this revision terminates the requirements of paragraph (i) of this AD. The revised Chapter 52 and 53 tasks replace the corresponding Chapter 52 and 53 tasks in Section 05–10– 17, ‘‘Structurally Significant Items (SSIs),’’ dated July 15, 2004, of the British Aerospace ATP AMM, as specified in paragraph (h) of this AD. Do the initial inspection for fatigue cracking at the applicable time in Part N., ‘‘Approval,’’ of BAE SYSTEMS (Operations) Limited Inspection Service Bulletin ATP–51– 002, Revision 3, dated April 3, 2008. (o) Except as provided by paragraph (q) of this AD: After the action specified in paragraph (n) of this AD has been accomplished, no alternative inspections or inspection intervals may be approved for the structural elements specified in the documents listed in paragraph (n) of this AD. (p) Submit a report of the findings (both positive and negative) of all of the inspections required by paragraph (n) of this AD to Customer Engineering Liaison, BAE SYSTEMS Regional Aircraft, Prestwick International Airport, Ayrshire, KA9 2RW, Scotland; telephone: +44 (0) 1292 675289; fax: +44 (0) 1292 675432; at the applicable time specified in paragraph (p)(1) or (p)(2) of this AD. The report must include the inspection results, a description of any discrepancies found, the airplane serial number, and the number of landings and flight hours on the airplane. (1) If the inspection was done on or after the effective date of this AD: Submit the report within 30 days after the inspection. (2) If the inspection was done before the effective date of this AD: Submit the report within 30 days after the effective date of this AD. International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057– 3356; telephone (425) 227–1175; fax (425) 227–1149. Before using any approved AMOC on any airplane to which the AMOC applies, notify your principal maintenance inspector (PMI) or principal avionics inspector (PAI), as appropriate, or lacking a principal inspector, your local Flight Standards District Office. The AMOC approval letter must specifically reference this AD. (2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service. (3) Reporting Requirements: For any reporting requirement in this AD, under the provisions of the Paperwork Reduction Act (44 U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120–0056. FAA AD Differences Related Information Note 5: This AD differs from the MCAI and/or service information as follows: No differences. (r) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2009–0074, dated March 31, 2009; and BAE SYSTEMS (Operations) Limited Inspection Service Bulletin ATP–51–002, Revision 3, dated April 3, 2008; for related information. Other FAA AD Provisions (q) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Todd Thompson, Material Incorporated by Reference (s) You must use the service information contained in Table 1 of this AD, as applicable, to do the actions required by this AD, unless the AD specifies otherwise. TABLE 1—ALL MATERIAL INCORPORATED BY REFERENCE Document Revision BAE SYSTEMS (Operations) Limited Service Bulletin ATP–51–002 .................................... BAE SYSTEMS (Operations) Limited Service Bulletin ATP–51–002 .................................... 3 ................................ Original ...................... (1) The Director of the Federal Register approved the incorporation by reference of the service information contained in Table 2 Date April 3, 2008. December 20, 2005. of this AD under 5 U.S.C. 552(a) and 1 CFR part 51. TABLE 2—NEW MATERIAL INCORPORATED BY REFERENCE Document Revision jlentini on DSKJ8SOYB1PROD with RULES BAE SYSTEMS (Operations) Limited Service Bulletin ATP–51–002 ................................................ (2) The Director of the Federal Register previously approved the incorporation by reference of the service information Date 3 April 3, 2008. contained in Table 3 of this AD on September 21, 2006 (71 FR 52418, September 6, 2006). TABLE 3—MATERIAL PREVIOUSLY INCORPORATED BY REFERENCE Document Revision BAE SYSTEMS (Operations) Limited Service Bulletin ATP–51–002 .................................... Original ...................... VerDate Nov<24>2008 16:14 Feb 24, 2010 Jkt 220001 PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 E:\FR\FM\25FER1.SGM 25FER1 Date December 20, 2005. Federal Register / Vol. 75, No. 37 / Thursday, February 25, 2010 / Rules and Regulations (3) For service information identified in this AD, contact BAE SYSTEMS Regional Aircraft, 13850 McLearen Road, Herndon, Virginia 20171; telephone 703–736–1080; email raebusiness@baesystems.com; Internet https://www.baesystems.com/Businesses/ RegionalAircraft/index.htm. (4) You may review copies of the service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information on the availability of this material at the FAA, call 425–227–1221 or 425–227–1152. (5) You may also review copies of the service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: https://www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on February 16, 2010. Stephen P. Boyd, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2010–3470 Filed 2–24–10; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2010–0131; Directorate Identifier 2009–NM–132–AD; Amendment 39–16216; AD 2010–05–07] RIN 2120–AA64 Airworthiness Directives; Airbus Model A340–200 and A340–300 Series Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. jlentini on DSKJ8SOYB1PROD with RULES SUMMARY: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: A review of A340 missions has demonstrated that CFM56–5C forward engine mount thrust links fitted with oversized bearing[s] will not reach the updated link fatigue life limit of 15500 Flight Cycles (FC) due to an increase in bore diameter. * * * The consequent potential failure of the affected thrust link would reduce the forward engine mounts’ structural integrity VerDate Nov<24>2008 16:14 Feb 24, 2010 Jkt 220001 and could eventually lead to engine separation, constituting an unsafe condition. * * * * * This AD requires actions that are intended to address the unsafe condition described in the MCAI. DATES: This AD becomes effective March 12, 2010. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of March 12, 2010. We must receive comments on this AD by April 12, 2010. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: (202) 493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–40, 1200 New Jersey Avenue, SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (800) 647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–1138; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: Discussion The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA Airworthiness Directive 2009–0108, dated May 5, 2009 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: A review of A340 missions has demonstrated that CFM56–5C forward engine PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 8471 mount thrust links fitted with oversized bearing[s] will not reach the updated link fatigue life limit of 15,500 Flight Cycles (FC) due to an increase in bore diameter. Oversized bearing repairs have been possible through the accomplishment of CMM 71–21–12 Repair 1. The consequent potential failure of the affected thrust link would reduce the forward engine mounts’ structural integrity and could eventually lead to engine separation, constituting an unsafe condition. Consequently, this AD requires: —The [detailed] inspection of the link assembly to identify a possible oversized bearing repair and, in case of finding, the application of the associated corrective actions, or —The repetitive [detailed] inspection [for cracking, damage (e.g., dents), and missing fasteners] of the forward engine mounts until accomplishment of the inspection of the link assembly for the identification of a possible oversized bearing repair. The corrective actions for finding oversized bearings in the forward engine mount thrust link assembly include contacting Goodrich for instructions and doing the repair. The corrective actions for finding cracking, damage (e.g., dents), and missing fasteners in the forward engine mounts include, depending on the findings, replacing cracked parts and missing fasteners, and polishing damaged areas. You may obtain further information by examining the MCAI in the AD docket. Relevant Service Information Airbus has issued Mandatory Service Bulletin A340–71–4007, including Appendix 1, dated April 1, 2009. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. FAA’s Determination and Requirements of This AD This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are issuing this AD because we evaluated all pertinent information and determined the unsafe condition exists and is likely to exist or develop on other products of the same type design. There are no products of this type currently registered in the United States. However, this rule is necessary to ensure that the described unsafe condition is addressed if any of these products are placed on the U.S. Register in the future. E:\FR\FM\25FER1.SGM 25FER1

Agencies

[Federal Register Volume 75, Number 37 (Thursday, February 25, 2010)]
[Rules and Regulations]
[Pages 8467-8471]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-3470]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-0130; Directorate Identifier 2009-NM-087-AD; 
Amendment 39-16214; AD 2010-05-05]
RIN 2120-AA64


Airworthiness Directives; BAE SYSTEMS (Operations) Limited Model 
ATP Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule; request for comments.

-----------------------------------------------------------------------

SUMMARY: We are adopting a new airworthiness directive (AD) for the 
products listed above that would supersede an existing AD. This AD 
results from mandatory continuing airworthiness information (MCAI) 
originated by an aviation authority of another country to identify and 
correct an unsafe condition on an aviation product. The MCAI describes 
the unsafe condition as:

    A review of the results of the final fuselage fatigue test 
identified the need for additional and revised safety-related 
fatigue- and environmental inspections for the fuselage. These 
additional tasks were introduced by Service Bulletin (SB) ATP-51-002 
* * *.
    As it was determined that these inspections were necessary to 
maintain the structural integrity of the aeroplane, EASA AD 2006-
0090 [which corresponds to FAA AD 2007-15-08] was issued * * *.
    Since the original Issue of the SB, three revisions have been 
published. Revision 1 of the SB included only editorial changes. 
Revision 2 of the SB corrected the fuselage frame designations in 
Parts 50 and 50A and extended the allowable time before initial 
inspection. In addition, the repeat inspection interval in Part 43 
of the SB was reduced. In the latest Revision 3 of the SB, the grace 
period for the initial inspection in Part 50 has been clarified.
* * * * *
The unsafe condition is fatigue cracking of certain structural 
elements, which could result in reduced structural integrity of the 
airplane and consequent rapid decompression of the airplane. This AD 
requires actions that are intended to address the unsafe condition 
described in the MCAI.

DATES: This AD becomes effective March 12, 2010.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of March 12, 
2010.
    On September 21, 2006 (71 FR 52418, September 6, 2006), the 
Director of the Federal Register approved the incorporation by 
reference of a certain other publication listed in this AD.
    We must receive comments on this AD by April 12, 2010.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: (202) 493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-40, 1200 New 
Jersey Avenue, SE., Washington, DC, between 9 a.m. and 5 p.m., Monday 
through Friday, except Federal holidays.

Examining the AD Docket

    You may examine the AD docket on the Internet at https://www.regulations.gov; or in person at the Docket Operations office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this AD, the regulatory evaluation, 
any comments received, and other information. The street address for 
the Docket Operations office (telephone (800) 647-5527) is in the 
ADDRESSES section. Comments will be available in the AD docket shortly 
after receipt.

FOR FURTHER INFORMATION CONTACT: Todd Thompson, International Branch, 
ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., 
Renton, Washington 98057-3356; telephone (425) 227-1175; fax (425) 227-
1149.

SUPPLEMENTARY INFORMATION:

Discussion

    On July 15, 2007, we issued AD 2007-15-08, Amendment 39-15137 (72 
FR 40230, July 24, 2007). That AD required actions intended to address 
an unsafe condition on the products listed above.
    Since we issued AD 2007-15-08, the European Aviation Safety Agency 
(EASA), which is the Technical Agent for the Member States of the 
European Community, has issued EASA Airworthiness Directive 2009-0074, 
dated March 31, 2009 (referred to after this as ``the MCAI''), to 
correct an unsafe condition for the specified products. The MCAI 
states:

    A review of the results of the final fuselage fatigue test 
identified the need for additional and revised safety-related 
fatigue- and environmental inspections for the fuselage. These 
additional tasks were introduced by Service Bulletin (SB) ATP-51-
002, which supplemented and in some cases revised those previously 
published in the Aircraft Maintenance Manual (AMM) Chapter 05-10-17 
and the Maintenance Review Board Report (MRBR).
    As it was determined that these inspections were necessary to 
maintain the structural integrity of the aeroplane, EASA AD 2006-
0090 [which corresponds to FAA AD 2007-15-08] was issued to require 
the inspections and, depending on findings, corrective actions as 
defined in BAE Systems (Operations) Limited SB ATP-51-002 (the SB) 
at original issue.
    Since the original Issue of the SB, three revisions have been 
published. Revision 1 of the SB included only editorial changes. 
Revision 2 of the SB corrected the fuselage frame designations in 
Parts 50 and 50A and extended the allowable time before initial

[[Page 8468]]

inspection. In addition, the repeat inspection interval in Part 43 
of the SB was reduced. In the latest Revision 3 of the SB, the grace 
period for the initial inspection in Part 50 has been clarified.
    Fatigue tasks in Parts 1 through 50 of the SB, i.e. those 
without an ``A'' suffix, have now been replicated in AMM Chapter 05-
10-17 and MRBR Section 6. In addition, environmental tasks, those 
identified with an ``A'' suffix, have now been replicated in MRBR 
Section 6.
    For the reasons described above, this AD retains the 
requirements of EASA AD 2006-0090, which is superseded, and requires 
the accomplishment of the inspections and, depending on findings, 
corrective actions as defined in BAE Systems (Operations) Limited SB 
ATP-51-002 at Revision 3.

The unsafe condition is fatigue cracking of certain structural 
elements, which could result in reduced structural integrity of the 
airplane and consequent rapid decompression of the airplane. The 
corrective actions include repairing cracking and corrosion, and 
depending on findings, repairing or replacing damaged components. You 
may obtain further information by examining the MCAI in the AD docket.

Relevant Service Information

    BAE SYSTEMS (Operations) Limited has issued Service Bulletin ATP-
51-002, Revision 3, dated April 3, 2008. The actions described in this 
service information are intended to correct the unsafe condition 
identified in the MCAI.

FAA's Determination and Requirements of This AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with the State of Design Authority, we have 
been notified of the unsafe condition described in the MCAI and service 
information referenced above. We are issuing this AD because we 
evaluated all pertinent information and determined the unsafe condition 
exists and is likely to exist or develop on other products of the same 
type design.
    There are no products of this type currently registered in the 
United States. However, this rule is necessary to ensure that the 
described unsafe condition is addressed if any of these products are 
placed on the U.S. Register in the future.

Differences Between the AD and the MCAI or Service Information

    We have reviewed the MCAI and related service information and, in 
general, agree with their substance. But we might have found it 
necessary to use different words from those in the MCAI to ensure the 
AD is clear for U.S. operators and is enforceable. In making these 
changes, we do not intend to differ substantively from the information 
provided in the MCAI and related service information.
    We might also have required different actions in this AD from those 
in the MCAI in order to follow FAA policies. Any such differences are 
highlighted in a NOTE within the AD.

Change to Existing AD

    This AD retains all requirements of AD 2007-15-08. Since AD 2007-
15-08 was issued, the AD format has been revised, and certain 
paragraphs have been rearranged. As a result, the corresponding 
paragraph identifiers have changed in this AD, as listed in the 
following table:

                      Revised Paragraph Identifiers
------------------------------------------------------------------------
                                      Corresponding requirement in this
    Requirement in AD 2007-15-08                      AD
------------------------------------------------------------------------
             paragraph (f)                       paragraph (g).
             paragraph (g)                       paragraph (h).
             paragraph (h)                       paragraph (i).
             paragraph (i)                       paragraph (j).
             paragraph (j)                       paragraph (k).
             paragraph (k)                       paragraph (l).
------------------------------------------------------------------------

FAA's Determination of the Effective Date

    Since there are currently no domestic operators of this product, 
notice and opportunity for public comment before issuing this AD are 
unnecessary.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not precede it by notice and opportunity for public 
comment. We invite you to send any written relevant data, views, or 
arguments about this AD. Send your comments to an address listed under 
the ADDRESSES section. Include ``Docket No. FAA-2010-0130; Directorate 
Identifier 2009-NM-087-AD'' at the beginning of your comments. We 
specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of this AD. We will consider all 
comments received by the closing date and may amend this AD because of 
those comments.
    We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this AD.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. ``Subtitle VII: Aviation 
Programs,'' describes in more detail the scope of the Agency's 
authority.
    We are issuing this rulemaking under the authority described in 
``Subtitle VII, Part A, Subpart III, Section 44701: General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We determined that this AD will not have federalism implications 
under Executive Order 13132. This AD will not have a substantial direct 
effect on the States, on the relationship between the national 
government and the States, or on the distribution of power and 
responsibilities among the various levels of government.
    For the reasons discussed above, I certify this AD:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979); and
    3. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this AD and placed it in the AD docket.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.

[[Page 8469]]

Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by removing Amendment 39-15137 (72 FR 
40230, July 24, 2007) and adding the following new AD:

2010-05-05 BAE Systems (Operations) Limited: Amendment 39-16214. 
Docket No. FAA-2010-0130; Directorate Identifier 2009-NM-087-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective March 
12, 2010.

Affected ADs

    (b) This AD supersedes AD 2007-15-08, Amendment 39-15137.

Applicability

    (c) This AD applies to all BAE Systems (Operations) Limited 
Model ATP airplanes, certificated in any category.

    Note 1: This AD requires revisions to certain operator 
maintenance documents to include new and revised inspections. 
Compliance with these inspections is required by 14 CFR 91.403(c). 
For airplanes that have been previously modified, altered, or 
repaired in the areas addressed by these inspections, the operator 
may not be able to accomplish the inspections described in the 
revisions. In this situation, to comply with 14 CFR 91.403(c), the 
operator must request approval for an alternative method of 
compliance according to paragraph (q) of this AD. The request should 
include a description of changes to the required inspections that 
will ensure the continued damage tolerance of the affected 
structure. The FAA has provided guidance for this determination in 
Advisory Circular (AC) 25-1529.

Subject

    (d) Air Transport Association (ATA) of America Code: 51: 
Standard Practices/Procedures.

Reason

    (e) The mandatory continued airworthiness information (MCAI) 
states:

    A review of the results of the final fuselage fatigue test 
identified the need for additional and revised safety-related 
fatigue- and environmental inspections for the fuselage. These 
additional tasks were introduced by Service Bulletin (SB) ATP-51-
002, which supplemented and in some cases revised those previously 
published in the Aircraft Maintenance Manual (AMM) Chapter 05-10-17 
and the Maintenance Review Board Report (MRBR).
    As it was determined that these inspections were necessary to 
maintain the structural integrity of the aeroplane, EASA AD 2006-
0090 [which corresponds to FAA AD 2007-15-08] was issued to require 
the inspections and, depending on findings, corrective actions as 
defined in BAE Systems (Operations) Limited SB ATP-51-002 (the SB) 
at original issue.
    Since the original Issue of the SB, three revisions have been 
published. Revision 1 of the SB included only editorial changes. 
Revision 2 of the SB corrected the fuselage frame designations in 
Parts 50 and 50A and extended the allowable time before initial 
inspection. In addition, the repeat inspection interval in Part 43 
of the SB was reduced. In the latest Revision 3 of the SB, the grace 
period for the initial inspection in Part 50 has been clarified.
    Fatigue tasks in Parts 1 through 50 of the SB, i.e. those 
without an ``A'' suffix, have now been replicated in AMM Chapter 05-
10-17 and MRBR Section 6. In addition, environmental tasks, those 
identified with an ``A'' suffix, have now been replicated in MRBR 
Section 6.
    For the reasons described above, this AD retains the 
requirements of EASA AD 2006-0090, which is superseded, and requires 
the accomplishment of the inspections and, depending on findings, 
corrective actions as defined in BAE Systems (Operations) Limited SB 
ATP-51-002 at Revision 3.

The unsafe condition is fatigue cracking of certain structural 
elements, which could result in reduced structural integrity of the 
airplane and consequent rapid decompression of the airplane. The 
corrective actions include repairing cracking and corrosion, and 
depending on findings, repairing or replacing damaged components.

Compliance

    (f) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.

Restatement of Requirements of AD 2006-18-09, With Revised Compliance 
Method

Airworthiness Limitations Revision Specified in AD 2000-26-10

    (g) Within 30 days after February 7, 2001 (the effective date of 
AD 2000-26-10, Amendment 39-12060, which was superseded by AD 2005-
19-03, which was superseded by AD 2007-15-08), revise the 
Airworthiness Limitations Section (ALS) of the Instructions for 
Continued Airworthiness according to a method approved by the 
Manager, International Branch, ANM-116, Transport Airplane 
Directorate, FAA. Doing the revision specified in paragraph (h) of 
this AD replaces Chapters 27, 32, 53, and 54 listed in Section 05-
10-11 and Chapters 52, 53, 54, 55, and 57 listed in Section 05-10-17 
that are in effect on February 7, 2001, with Chapters 27, 32, 53, 
and 54 listed in Section 05-10-11, ``Mandatory Life Limitations 
(Airframe)''; and Chapters 52, 53, 54, 55, and 57 listed in Section 
05-10-17, ``Structurally Significant Items (SSIs)''; both dated July 
15, 2004; of the British Aerospace ATP Aircraft Maintenance Manual 
(AMM). Doing the revision specified in paragraph (l) of this AD 
replaces Sections 05-10-12, 05-10-15, and 05-10-17 with the 
corresponding sections specified in paragraph (l) of this AD.

    Note 2: Guidance on revising the ALS can be found in Section 05-
00-00, dated August 15, 1997, of the British Aerospace ATP AMM, 
dated October 15, 1999. This section references other chapters of 
the AMM. The applicable revision level of the referenced chapters is 
that in effect on February 7, 2001.

Airworthiness Limitations Specified in AD 2005-19-03

    (h) Within 30 days after September 28, 2005 (the effective date 
of AD 2005-19-03, Amendment 39-14268, which was superseded by AD 
2006-18-09), revise the ALS of the Instructions for Continued 
Airworthiness according to a method approved by the Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA. 
Doing the revision specified in paragraph (i) of this AD replaces 
certain Chapter 52 and 53 tasks listed in Section 05-10-17, 
``Structurally Significant Items (SSIs),'' dated July 15, 2004, of 
the British Aerospace ATP AMM, with the corresponding Chapter 52 and 
53 tasks listed in BAE SYSTEMS (Operations) Limited Service Bulletin 
ATP-51-002, dated December 20, 2005. Doing the revision specified in 
paragraph (l) of this AD replaces Chapters 52, 53, 54, 55, and 57 
listed in Section 05-10-17 with the corresponding Section 05-10-17 
specified in paragraph (l) of this AD.

    Note 3: Guidance on revising the ALS can be found in Chapters 
27, 32, 53, and 54 listed in Section 05-10-11, ``Mandatory Life 
Limitations (Airframe)''; and the tasks for Chapters 52, 53, 54, 55, 
and 57 listed in Section 05-10-17, ``Structurally Significant Items 
(SSIs)''; both dated July 15, 2004; of the British Aerospace ATP 
AMM. These chapters replace the corresponding chapters in Section 
05-00-00, dated August 15, 1997, of the British Aerospace ATP AMM as 
specified in paragraph (g) of this AD.

New and Revised Airworthiness Limitations in AD 2006-18-09

    (i) Within 30 days after September 21, 2006 (the effective date 
of AD 2006-18-09), revise the ALS of the Instructions for Continued 
Airworthiness by incorporating the new and revised tasks for 
Chapters 52 and 53 as specified in BAE SYSTEMS (Operations) Limited 
Service Bulletin ATP-51-002, dated December 20, 2005, into the ALS. 
The revised Chapter 52 and 53 tasks replace the corresponding 
Chapter 52 and 53 tasks in Section 05-10-17, ``Structurally 
Significant Items (SSIs),'' dated July 15, 2004, of the British 
Aerospace ATP AMM, as specified in paragraph (h) of this AD.
    (j) Except as provided by paragraph (q) of this AD: After the 
actions specified in paragraphs (g), (h), and (i) of this AD have 
been accomplished, no alternative inspections or inspection 
intervals may be approved for the structural elements specified in 
the documents listed in paragraphs (g), (h), and (i) of this AD.

No Reporting Required

    (k) Although BAE SYSTEMS (Operations) Limited Service Bulletin 
ATP-51-002, dated December 20, 2005, specifies to submit certain 
information to the manufacturer, this AD does not include that 
requirement.

Restatement of Requirements of AD 2007-15-08, With Revised Compliance 
Method

Revised Limitations

    (l) Within 30 days after August 8, 2007 (the effective date of 
AD 2007-15-08), revise the

[[Page 8470]]

ALS of the Instructions for Continued Airworthiness according to a 
method approved by the Manager, International Branch, ANM-116, 
Transport Airplane Directorate, FAA.

    Note 4: Guidance on revising the ALS can be found in Section 05-
10-12, ``Mandatory Life Limitations (Airframe--Structures),'' dated 
January 15, 2007; Section 05-10-15, ``Mandatory Life Limitations 
(Powerplant/Engine/APU--Structures),'' dated January 15, 2007; and 
Section 05-10-17, ``Structurally Significant Items (SSIs),'' dated 
January 15, 2007; of the BAE Systems (Operations) Limited ATP AMM. 
The revised sections replace the corresponding sections specified in 
paragraphs (g) and (h) of this AD.

    (m) Except as provided by paragraph (q) of this AD: After the 
action specified in paragraph (l) of this AD has been accomplished, 
no alternative inspections or inspection intervals may be approved 
for the structural elements specified in the documents listed in 
paragraph (l) of this AD.

New Requirements of This AD

Actions

    (n) Within 30 days after the effective date of this AD: Revise 
the ALS of the Instructions for Continued Airworthiness by 
incorporating the inspections specified in BAE SYSTEMS (Operations) 
Limited Inspection Service Bulletin ATP-51-002, Revision 3, dated 
April 3, 2008. Doing this revision terminates the requirements of 
paragraph (i) of this AD. The revised Chapter 52 and 53 tasks 
replace the corresponding Chapter 52 and 53 tasks in Section 05-10-
17, ``Structurally Significant Items (SSIs),'' dated July 15, 2004, 
of the British Aerospace ATP AMM, as specified in paragraph (h) of 
this AD. Do the initial inspection for fatigue cracking at the 
applicable time in Part N., ``Approval,'' of BAE SYSTEMS 
(Operations) Limited Inspection Service Bulletin ATP-51-002, 
Revision 3, dated April 3, 2008.
    (o) Except as provided by paragraph (q) of this AD: After the 
action specified in paragraph (n) of this AD has been accomplished, 
no alternative inspections or inspection intervals may be approved 
for the structural elements specified in the documents listed in 
paragraph (n) of this AD.
    (p) Submit a report of the findings (both positive and negative) 
of all of the inspections required by paragraph (n) of this AD to 
Customer Engineering Liaison, BAE SYSTEMS Regional Aircraft, 
Prestwick International Airport, Ayrshire, KA9 2RW, Scotland; 
telephone: +44 (0) 1292 675289; fax: +44 (0) 1292 675432; at the 
applicable time specified in paragraph (p)(1) or (p)(2) of this AD. 
The report must include the inspection results, a description of any 
discrepancies found, the airplane serial number, and the number of 
landings and flight hours on the airplane.
    (1) If the inspection was done on or after the effective date of 
this AD: Submit the report within 30 days after the inspection.
    (2) If the inspection was done before the effective date of this 
AD: Submit the report within 30 days after the effective date of 
this AD.

FAA AD Differences

    Note 5: This AD differs from the MCAI and/or service information 
as follows: No differences.

Other FAA AD Provisions

    (q) The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, FAA, has the authority to approve AMOCs for 
this AD, if requested using the procedures found in 14 CFR 39.19. 
Send information to ATTN: Todd Thompson, International Branch, ANM-
116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., 
Renton, Washington 98057-3356; telephone (425) 227-1175; fax (425) 
227-1149. Before using any approved AMOC on any airplane to which 
the AMOC applies, notify your principal maintenance inspector (PMI) 
or principal avionics inspector (PAI), as appropriate, or lacking a 
principal inspector, your local Flight Standards District Office. 
The AMOC approval letter must specifically reference this AD.
    (2) Airworthy Product: For any requirement in this AD to obtain 
corrective actions from a manufacturer or other source, use these 
actions if they are FAA-approved. Corrective actions are considered 
FAA-approved if they are approved by the State of Design Authority 
(or their delegated agent). You are required to assure the product 
is airworthy before it is returned to service.
    (3) Reporting Requirements: For any reporting requirement in 
this AD, under the provisions of the Paperwork Reduction Act (44 
U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has 
approved the information collection requirements and has assigned 
OMB Control Number 2120-0056.

Related Information

    (r) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2009-0074, dated March 31, 2009; 
and BAE SYSTEMS (Operations) Limited Inspection Service Bulletin 
ATP-51-002, Revision 3, dated April 3, 2008; for related 
information.

Material Incorporated by Reference

    (s) You must use the service information contained in Table 1 of 
this AD, as applicable, to do the actions required by this AD, 
unless the AD specifies otherwise.

                                 Table 1--All Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
              Document                            Revision                                Date
----------------------------------------------------------------------------------------------------------------
BAE SYSTEMS (Operations) Limited     3................................  April 3, 2008.
 Service Bulletin ATP-51-002.
BAE SYSTEMS (Operations) Limited     Original.........................  December 20, 2005.
 Service Bulletin ATP-51-002.
----------------------------------------------------------------------------------------------------------------

     (1) The Director of the Federal Register approved the 
incorporation by reference of the service information contained in 
Table 2 of this AD under 5 U.S.C. 552(a) and 1 CFR part 51.

                                 Table 2--New Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
                   Document                       Revision                            Date
----------------------------------------------------------------------------------------------------------------
BAE SYSTEMS (Operations) Limited Service                    3  April 3, 2008.
 Bulletin ATP-51-002.
----------------------------------------------------------------------------------------------------------------

     (2) The Director of the Federal Register previously approved 
the incorporation by reference of the service information contained 
in Table 3 of this AD on September 21, 2006 (71 FR 52418, September 
6, 2006).


                             Table 3--Material Previously Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
              Document                            Revision                                Date
----------------------------------------------------------------------------------------------------------------
BAE SYSTEMS (Operations) Limited     Original.........................  December 20, 2005.
 Service Bulletin ATP-51-002.
----------------------------------------------------------------------------------------------------------------


[[Page 8471]]

     (3) For service information identified in this AD, contact BAE 
SYSTEMS Regional Aircraft, 13850 McLearen Road, Herndon, Virginia 
20171; telephone 703-736-1080; e-mail raebusiness@baesystems.com; 
Internet https://www.baesystems.com/Businesses/RegionalAircraft/index.htm.
    (4) You may review copies of the service information at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington. For information on the availability of this material at 
the FAA, call 425-227-1221 or 425-227-1152.
    (5) You may also review copies of the service information that 
is incorporated by reference at the National Archives and Records 
Administration (NARA). For information on the availability of this 
material at NARA, call 202-741-6030, or go to: https://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

    Issued in Renton, Washington, on February 16, 2010.
Stephen P. Boyd,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2010-3470 Filed 2-24-10; 8:45 am]
BILLING CODE 4910-13-P
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